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3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 1/8 Due Mar 24 at 11:59pm Points 100 Questions 25 Time Limit None Allowed Attempts Unlimited Instructions Attempt History Attempt Time Score LATEST Attempt 1 10 minutes 92 out of 100 Score for this attempt: 92 out of 100 Submitted Mar 24 at 4:37pm This attempt took 10 minutes.  Question 1 4 / 4 pts Correct! less stable at all speeds. less stable at slow speeds, but more stable at high speeds. less stable at high speeds, but more stable at low speeds. Loading in a tail-heavy condition can reduce the airplane's ability to recover from stalls and spins. Tail-heavy loading also produces very light stick forces at all speeds, making it easy for the pilot to inadvertently overstress the airplane.  This quiz can be taken as many times as desired . Answer the 25 multiple choice questions. Before you begin, make sure you have downloaded the FAA Airman Knowledge Testing Supplement Document (PDF) (https://www.faa.gov/training_testing/testing/supplements/media/sport_rec_private_akts.pdf) and are familiar with navigating its contents, as some of the Lab questions will reference its figures. Any reference to a figure in the quiz can be found in the Supplement Document. Time limit: There is no time limit for this lab. It is recommended that you use a 100-minute limit and at the end of 100 minutes, assess your status. You actual quiz in ASCI 121 will have a 100-minute limit and give a notification pop-up approximately 10 seconds before the time expires. If you encounter technical difficulties, please contact your instructor. Grading: You will see scores for multiple-choice questions right away. Please contact your instructor if you have any questions. Your score will be reflected by the highest score you attain . 1.1 Basic Aerodynamics Laboratory Quiz Take the Quiz Again Loading an airplane to the most aft CG will cause the airplane to be

3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 2/8 Question 2 4 / 4 pts Correct! Stalled. Partially stalled with one wing low. In a steep diving spiral. A spin results when a sufficient degree of rolling or yawing control input is imposed on an airplane in the stalled condition. If the wing is not stalled, a spin cannot occur.  Question 3 4 / 4 pts Correct! require less effort to control. not spin. be difficult to stall. A stable airplane will tend to return to the original condition of flight if disturbed by a force such as turbulent air. This means that a stable airplane is easy to fly.  Question 4 4 / 4 pts Correct! above and upwind from the heavy aircraft. below and upwind from the heavy aircraft. below and downwind from the heavy aircraft. When departing behind a large aircraft, note the large aircraft's rotation point, rotate prior to it, continue to climb above it, and request permission to deviate upwind of the large aircraft's climb path until turning clear of the aircraft's wake.  Question 5 4 / 4 pts Correct! nullify all attempts at accuracy in judgment of gliding distance and landing spot. assure the proper descent angle is maintained until entering the flare. increase the chances of shock cooling the engine. A constant gliding speed should be maintained because variations of gliding speed nullify all attempts at accuracy in judgment of gliding distance and the landing spot.  In what flight condition must an aircraft be placed in order to spin? An airplane said to be inherently stable will When departing behind a heavy aircraft, the pilot should avoid wake turbulence by maneuvering the aircraft When executing an emergency approach to land in a single-engine airplane, it is important to maintain a constant glide speed because variations in glide speed

3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 3/8 Question 6 4 / 4 pts Corners 1 and 2. Correct! Corners 1 and 4. Corners 2 and 4. The airplane will turn less than 90 degrees at corners 1 and 4. At corner 1, the airplane turns to a heading that is crabbed into the wind, which makes the turn less than 90 degrees. At corner 4, the airplane is crabbed into the wind when the turn is started, and the turn will be less than 90 degrees.  Question 7 4 / 4 pts Correct! The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced. The CG shifts forward when thrust and drag are reduced. When thrust is reduced to less than weight, lift is also reduced and the wings can no longer support the weight. The location of the center of gravity with respect to the center of lift determines to a great extent the longitudinal stability of an airplane. Center of gravity aft of the center of lift will result in an undesirable pitch-up moment during flight. An airplane with the center of gravity forward of the center of lift will pitch down when power is reduced. This will increase the airspeed and the downward force on the elevators. This increased downward force on the elevators will bring the nose up, providing positive stability. The farther forward the CG is, the more stable the airplane.  Question 8 0 / 4 pts An additional upward force is generated as the lower surface of the wing deflects air downward. Correct Answer Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface. You Answered For every action there is an equal and opposite reaction. Bernoulli's principle states in part that the pressure of a fluid (liquid or gas) decreases at points where the speed of the fluid increases. In other words, high-speed flow is associated with low pressure and low-speed flow with high pressure. Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface.  Question 9 4 / 4 pts Correct! Outward, upward, and around each tip. Inward, upward, and counterclockwise. Inward, upward, and around each tip. (Refer to figure 62.) In flying the rectangular course, when would the aircraft be turned less than 90°? What causes an airplane (except a T-tail) to pitch nosedown when power is reduced and controls are not adjusted? Which statement relates to Bernoulli`s principle? How does the wake turbulence vortex circulate around each wingtip?

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3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 4/8 The vortex circulation is outward, upward, and around the wing tips when viewed from either ahead or behind the aircraft.  Question 10 4 / 4 pts To decrease wing area to vary the lift. Correct! To enable the pilot to make steeper approaches to a landing without increasing the airspeed. To relieve the pilot of maintaining continuous pressure on the controls. Flaps increase drag, allowing the pilot to make steeper approaches without increasing airspeed.  Question 11 4 / 4 pts Correct! The horizontal component of lift. The vertical component of lift. Centrifugal force. As the airplane is banked, lift acts horizontally as well as vertically and the airplane is pulled around the turn.  Question 12 4 / 4 pts The result of an alteration in airflow patterns increasing induced drag about the wings of an airplane. Correct! The result of the interference of the surface of the Earth with the airflow patterns about an airplane. The result of the disruption of the airflow patterns about the wings of an airplane to the point where the wings will no longer support the airplane in flight. Ground effect is the result of the interference of the surface of the Earth with the airflow patterns about an airplane.  Question 13 4 / 4 pts 4,500 pounds. 7,200 pounds. Correct! 6,750 pounds. Referencing FAA Figure 2, use the following steps: 1. Enter the chart at a 45° angle of bank and proceed upward to the curved reference line. From the point of intersection, move to the left side of the chart and read a load factor of 1.5 Gs. 2. Multiply the aircraft weight by the load factor. 4,500 x 1.5 = 6,750 lbs Or, working from the table: 4,500 x 1.414 (load factor) = 6,363 lbs Answer B is the closest. What is one purpose of wing flaps? What force makes an airplane turn? What is ground effect? (Refer to Figure 2.) If an airplane weighs 4,500 pounds, what approximate weight would the airplane structure be required to support during a 45° banked turn while maintaining altitude?

3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 5/8  Question 14 4 / 4 pts lifting capacity. lift/drag ratio. Correct! aerodynamic balance and controllability. The center of pressure of an asymmetrical airfoil moves forward as the angle of attack is increased, and backward as the angle of attack is decreased. This backward and forward movement of the point at which lift acts, affects the aerodynamic balance and the controllability of the aircraft.  Question 15 4 / 4 pts Correct! Both wings are stalled. Only the left wing is stalled. Neither wing is stalled. One wing is less stalled than the other, but both wings are stalled in a spin.  Question 16 4 / 4 pts Correct! increase the angle of descent without increasing the airspeed. decrease the angle of descent without increasing the airspeed. permit a touchdown at a higher indicated airspeed. Flaps increase drag, allowing the pilot to make steeper approaches without increasing airspeed.  Question 17 4 / 4 pts rise into the takeoff or landing path of a crossing runway. Correct! sink below the aircraft generating turbulence. rise into the traffic pattern. Flight tests have shown that the vortices from large aircraft sink at a rate of about 400 to 500 feet per minute. They tend to level off at a distance about 900 feet below the path of the generating aircraft.  Changes in the center of pressure of a wing affect the aircraft`s During a spin to the left, which wing(s) is/are stalled? One of the main functions of flaps during approach and landing is to Wingtip vortices created by large aircraft tend to

3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 6/8 Question 18 4 / 4 pts twice the length of the wingspan above the surface. a higher-than-normal angle of attack. Correct! less than the length of the wingspan above the surface. When the wing is at a height equal to its span, the reduction in induced drag is only 1.4%. However, when the wing is at a height equal to one-fourth its span, the reduction in induced drag is 23.5% and when the wing is at a height equal to one-tenth its span, the reduction in induced drag is 47.6%.  Question 19 4 / 4 pts Correct! To control yaw. To control overbanking tendency. To control roll. The purpose of the rudder is to control yaw.  Question 20 4 / 4 pts increase if the CG is moved forward. change with an increase in gross weight. Correct! remain the same regardless of gross weight. When the angle of attack is increased to between 18° and 20° (critical angle of attack) on most airfoils, the airstream can no longer follow the upper curvature of the wing because of the excessive change in direction. The airplane will stall if the critical angle of attack is exceeded. The indicated airspeed at which stall occurs will be determined by weight and load factor, but the stall angle of attack is the same.  Question 21 4 / 4 pts 2,300 pounds. Correct! 4,600 pounds. 3,400 pounds. Referencing FAA Figure 2, use the following steps: 1. Enter the chart at a 60° angle of bank and proceed upward to the curved reference line. From the point of intersection, move to the left side of the chart and read a load factor of 2 Gs. 2. Multiply the aircraft weight by the load factor: 2,300 x 2 = 4,600 lbs Or, working from the table: 2,300 x 2.0 (load factor) = 4,600 lbs Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at What is the purpose of the rudder on an airplane? The angle of attack at which an airplane wing stalls will (Refer to Figure 2.) If an airplane weighs 2,300 pounds, what approximate weight would the airplane structure be required to support during a 60° banked turn while maintaining altitude?

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3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 7/8  Question 22 4 / 4 pts Stay below and to one side of its final approach flightpath. Correct! Stay above its final approach flightpath all the way to touchdown. Stay well below its final approach flightpath and land at least 2,000 feet behind. When landing behind a large aircraft, stay at or above the large aircraft's final approach path. Note its touchdown point and land beyond it.  Question 23 0 / 4 pts You Answered rise from a crossing runway into the takeoff or landing path. Correct Answer sink into the flightpath of aircraft operating below the aircraft generating the turbulence. rise into the traffic pattern area surrounding the airport. Flight tests have shown that the vortices from large aircraft sink at a rate of about 400 to 500 feet per minute. They tend to level off at a distance about 900 feet below the path of the generating aircraft.  Question 24 4 / 4 pts 3,100 pounds. Correct! 3,960 pounds. 1,200 pounds. Referencing FAA Figure 2, use the following steps: 1. Enter the chart at a 30° angle of bank and proceed upward to the curved reference line. From the point of intersection, move to the left side of the chart and read an approximate load factor of 1.2 Gs. 2. Multiply the aircraft weight by the load factor: 3,300 x 1.2 = 3,960 lbs Or, working from the table: 3,300 x 1.154 (load factor) = 3,808 lbs Answer C is the closest.  Question 25 4 / 4 pts light, quartering headwind. Correct! light, quartering tailwind. strong headwind. When landing behind a large aircraft, which procedure should be followed for vortex avoidance? When taking off or landing at an airport where heavy aircraft are operating, one should be particularly alert to the hazards of wingtip vortices because this turbulence tends to (Refer to Figure 2.) If an airplane weighs 3,300 pounds, what approximate weight would the airplane structure be required to support during a 30° banked turn while maintaining altitude? The wind condition that requires maximum caution when avoiding wake turbulence on landing is a

3/24/24, 1:38 PM 1.1 Laboratory Quiz: Basic Aerodynamics: ASCI 121L Airmen Knowledge Test Prep - Mar 2024 - Online https://erau.instructure.com/courses/170678/quizzes/599656 8/8 A tailwind condition can move the vortices of a preceding aircraft forward into the touchdown zone. A light quartering tailwind requires maximum caution. Pilots should be alert to large aircraft upwind from their approach and takeoff flight paths. Quiz Score: 92 out of 100